JPH09109999A - Radio controlled bi-plane - Google Patents

Abstract

PROBLEM TO BE SOLVED: To enhance maneuverability by letting a main wing be so constituted as to be made up of a sheet wing composed of a movable sheet member, which can be fixed to a frame in an expanded condition while being exposed to wind from the head, and of a rigid wing which is provided in prescribed place underneath the sheet wing with its one end mounted onto a fuselage. SOLUTION: When each of paired rigid wings 3 which are symmetrically located about a fuselage 1 at the center of them, is mounted onto the fuselage 1 at their one end, and is mounted onto the frame 2a of a sheet wing 2 or onto each place close to the aforesaid frame, each wing can be commonly used as a pole 4 supporting the sheet wing 2, the poles required from the standpoint of strength can thereby be lessened in number, the aircraft is lessened in weight, and the rigid wings can thereby be prevented from being damaged when the aircraft takes off and lands on. Besides, since the sheet wing 2 is formed out of a movable sheet member 2b, the sheet wing 2 is liable to be unstable aerodynamically because of its deformation when it is subjected to uneven load, however, the aforesaid unstable condition can be relaxed by the rigid wings 3. By this constitution, even when the aircraft flies at the high speed, its stability is excellent, and a speed range at which the aircraft can fly, can thereby be widened so as to be enhanced to a great extent.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a radio-controlled biplane in which the main wing is composed of a seat wing and a rigid wing, whose control is remotely controlled by radio, has a wide range of stable flight speed, and has excellent controllability. It's about airplanes.

[0002]

2. Description of the Related Art In the event of a disaster, on-site shooting, observation, search, rescue assistance, wireless relay, etc., topographical survey in power transmission line construction, extension of pilot rope, transportation of lightweight small articles, etc. At that time, manned or unmanned aircraft have been conventionally used.

As a conventional manned aircraft used for such a purpose, a relatively large aircraft is used because it is necessary to mount various equipments and articles necessary for pilots, workers, and work, and takeoff and landing. Since the place is limited to a vast place such as an airport, there is often a case where there is no suitable takeoff and landing place near the site where the above-mentioned various works are performed, and there is a drawback that the efficiency is very poor. In addition, the manned aircraft itself is expensive and requires a pilot with special skills, so the work cost is high, and when flying over the site of a fire or eruption, the flight environment such as the air flow is unstable, When poisonous gas is generated, there is a problem in the health of passengers, and in the case of a crash, there is a disadvantage that a fatal accident with a high mortality rate results. When the manned aircraft is an airplane, the structure has a high stall speed, which makes it difficult to fly at low speed, and it is difficult to use it depending on the work.

For this reason, as an unmanned aircraft,
Unmanned airplanes and helicopters that are remotely controlled by radio are widely used. The former unmanned aerial vehicle has long fixed wings with sideways protruding, so it has a high stall speed and is difficult to fly at a low speed as in the case of the manned aircraft. However, there are drawbacks in that it is difficult to take pictures and observe the images, and the mobility is poor and the working efficiency is reduced. Further, in the case where the propeller is located at the leading edge of the main wing or the nose when it is accidentally landed due to stall or the like during flight, there is a drawback that the propeller comes into contact with structures or people on the ground and is very dangerous.

The latter unmanned helicopter is capable of vertical takeoff and landing and air stop, but its operation is extremely difficult and requires skill, and since a large propeller is attached to the main rotor, it can be used in case of emergency landing. There was a risk that this propeller would come into contact with structures and people, resulting in a very dangerous accident.

Therefore, the present applicants proposed a radio controlled aircraft (see Japanese Patent Laid-Open No. 7-40897) which can solve the above-mentioned drawbacks of manned and unmanned aircraft. Briefly, this radio-controlled aircraft consists of a front end of a central girder member fixed above the fuselage by a pillar fixed to the fuselage and a vertical stabilizer and a beam member fixed to this central girder member. It is fixed to the side girders provided on both ends with a substantially V shape in a plane, and fixed to the central girder and side girders so that they can be inflated by receiving wind from the front. A main wing component composed of a main wing sheet made of a flexible material is used as a main wing, and a vertical tail having a rudder at the rear end of the fuselage and a horizontal tail serving as an elevator are provided and located near the center of gravity of the airframe. It is a radio controlled aircraft equipped with a prime mover that rotates a propeller that is used.

Since the main wing area is large relative to the weight of the airframe in this radio-controlled aircraft, the lift required for flight can be obtained even at low speeds where the load acting per unit area of the main wing is small, so low speed flight is possible. In addition to being possible, the approach angle at takeoff and landing can be made steep, there is almost no restriction on takeoff and landing, gliding is possible, the risk of crash is low, and the propeller is located near the center of gravity of the aircraft. Therefore, it is possible to prevent the propeller from contacting the ground object and it is excellent in safety, easy to maneuver and excellent in maneuverability, it is possible to work efficiently in the sky, and depending on the weather conditions. It has various effects such as being able to stop in the air and efficiently performing work in the air.

However, the radio-controlled aircraft has a problem in stability during high-speed flight. In particular, a state in which the posture of the body is collapsed when a cross wind is received is restored to a normal state (hereinafter, roll axis control is performed). As a means for doing so, the operation of the rudder of the vertical tail and the left and right independent aileron-like operation of the horizontal tail that functions as an elevator are performed. However, there is a drawback in that it is not possible to obtain a sufficient force to restore the roll, and the control of the roll axis is slow.

[0009]

SUMMARY OF THE INVENTION An object of the present invention is to solve the above-mentioned drawbacks of the prior art and to provide a radio-controlled biplane aircraft which has a wide speed range in which stable flight is possible and is excellent in maneuverability.

[0010]

Means for Solving the Problems As a result of intensive studies to solve the above problems, the present inventors have fixed the upper part of the fuselage to the upper center of the fuselage by means of a pillar and a vertical stabilizer that are fixed to the fuselage. A center girder member having a mounting surface that is raised and slopes downward in a substantially straight line as it goes backward,
It is fixed to both ends of the pillar fixed to the body and the beam fixed to the central girder and the front end of the central girder, respectively. And a frame made up of side girders that incline downward in a substantially straight line as it goes rearward, and a seat wing made of a flexible sheet material that is fixed to the frame so as to expand in response to wind from the front. , The main wing is composed of a rigid wing attached at one end to the fuselage and provided at a predetermined position below the seat wing, and laterally to a fixed wing fixed upright to the rear end of the fuselage. A vertical tail with a rudder attached so that it can swing, a horizontal tail with the entire wings swingably attached to a fixed wing of this vertical tail about a horizontal axis laterally, and a state in which it is integral with the fuselage The prime mover inside the prime mover case If a propeller that is rotated near the center of gravity of the airframe is provided and the output of the prime mover, the swing angle of the rudder of the vertical tail and the swing angle of the horizontal tail are controlled wirelessly, stable The present invention has been completed by clarifying that the stability in high-speed flight can be improved as compared with the conventional radio-controlled airplane that has various effects in which the flight speed is wide and the main wing is composed of only the seat wing. Of.

Further, the rigid wings are provided so that their angles of attack can be controlled independently of each other on both the left and right sides of the body, and the auxiliary wings can be controlled independently of each other on the left and right sides of the body. If it is provided, the roll axis can be quickly controlled and the maneuverability can be greatly improved, and the other end of the rigid wing whose one end is fixed to the body is the seat wing. If it is attached to the side edge of the frame or its vicinity, the weight of the aircraft can be reduced and the storage volume of the mounted equipment can be secured as wide as possible, and the rigid wing can be attached to the fuselage. It was also clarified that it is preferable that the position is set to a prime mover case that is integrated with the upper part of the fuselage body via a frame, because damage to the rigid wings can be prevented even if the posture during takeoff and landing is somewhat banked.

[0012]

BEST MODE FOR CARRYING OUT THE INVENTION A radio control biplane according to the present invention will be described in detail below with reference to an embodiment shown in the drawings. 1 is an explanatory plan view showing an embodiment of a radio-controlled biplane aircraft according to the present invention, FIG. 2 is a side view of FIG. 1, FIG. 3 is a front view of FIG. 1, and FIG. 4 is a radio-controlled plane of the present invention. It is explanatory drawing which shows the rigid blade in another Example.

In the drawings, reference numeral 1 designates a body, and a case in which a later-described prime mover case 7 is integrated through a frame as in the illustrated embodiment is also referred to as a body 1. 2 is the body 1
A central girder 2aa, which is fixed to the upper center of the body 1 by a pillar 4 and a vertical tail 5, which are fixed to the upper part of the body 1 and has a mounting surface that swells up high in the front and inclines downward substantially linearly toward the rear. , The pillar 4 fixed to the body 1 and the beam 2ac fixed to the central girder 2aa and the front end of the central girder 2aa, respectively, are fixed to both sides in a plane in a substantially V shape. Side girder material that is symmetric and forms a substantially straight downward slope as it goes rearward
Frame 2a consisting of 2ab, and this frame 2a is fixed in a state that it swells by receiving wind from the front, it has excellent tensile strength and water resistance and is coated with a lightweight rubber or plastic that reliably receives wind from the front A sheet wing made of a flexible sheet material 2b, which is preferably a synthetic fiber cloth,

Reference numeral 3 denotes a rigid wing having one end attached to the body 1 and provided at a predetermined position below the seat wing 2. The seat wing 2 and the rigid wing 3 constitute a main wing. .

At least one rigid wing 3 is symmetrically projected on each side of the body 1, and the number may be plural.
Basically, it only needs to be one. Specifically, as shown in FIG. 1, one rigid wing 3 sandwiching the fuselage 1 symmetrically is attached to the fuselage 1 at one end and the frame 2a of the seat wing 2 at the other end or in the vicinity thereof. Since it is commonly used as the support column 4 for supporting the seat wing 2, the number of support columns required for strength can be reduced, the weight of the aircraft is reduced, and the dihedral angle is large, so the posture during takeoff and landing is somewhat banked. Even if it does, damage to the rigid blade 3 is prevented, which is preferable. In order to exert such an effect more effectively, the prime mover case in which the mounting position of the rigid wing 3 on the body 1 is integrated with the upper part of the body of the body via a frame as in the embodiment shown in FIG. A value of 7 is more preferable because the rigid blade 3 is located at a position considerably higher than the lower surface of the body 1.

The rigid wings 3 are provided so that their angles of attack can be controlled independently of each other on the left and right sides of the body 1, or can be controlled independently of each other on the left and right sides of the body 1. It is preferable that the auxiliary blade 3a is provided, and by controlling the angle of attack of the auxiliary blade 3a or the rigid blade 3 in this manner, the roll axis can be quickly controlled.

Reference numeral 5 denotes a vertical stabilizer having a rudder 5b swingably laterally mounted on a fixed blade 5a which is vertically fixed to the rear end of the body 1, and 6 denotes a fixed blade 5a of the vertical stabilizer 5. A horizontal stabilizer with the entire wing swingably mounted around a horizontal axis on the side, 7 is provided in a state of being integrated with the fuselage 1, and a prime mover case in which the mounted prime mover is housed, 8 Is a propeller that is rotated by the rotation of the output shaft of the prime mover in the prime mover case 7, is located near the center of gravity of the fuselage, and is further provided with a propeller guide 8a at a position surrounding the outer periphery of the rotation trajectory of the tip. Is preferably provided.

Although not shown, the angle of attack control of the rigid wing 3 or the auxiliary wing control when the auxiliary wing 3a is provided, the control of the rudder 5b of the vertical tail 5, the horizontal tail 6 serving as an elevator. And a power transmission mechanism for transmitting the power of the servomotor to each of the controlled parts, which is generally used in a conventional radio-controlled aircraft whose flight is controlled by radio to control the output of the motor and the output of the prime mover. And a wireless receiver that receives a signal from a wireless transmitter and controls the servo motor.

In the radio-controlled biplane aircraft according to the present invention having such a configuration, the main wing is the seat wing 2 and the rigid wing 3.
Since it is composed of and, at the time of takeoff, not only can the lift required for flight be obtained even at low speeds where the load per unit area of the main wing is small, but also the stall speed is low, so a long runway can be used. If it is not necessary and the weight of the airframe is light enough to be lifted by human power, it is possible to take off even if thrown upwind by human power, and there is almost no restriction on the takeoff location.

During flight, since the stall speed is low, the stability of low-speed flight is good, the glide is possible, and the autonomous posture restoring force is excellent, and the flight is easy. Further, at the time of high-speed flight, since the seat wing 2 is made of the flexible sheet material 2b, the rigid wing 3 is used to alleviate the unstable state caused by the deformation of the seat wing 2 which causes uneven load on the seat wing 2. Therefore, stability in high speed flight is improved.

The rigid wings 3 are independently provided on both sides of the body 1 so that the angle of attack of the rigid wings 3 can be controlled independently, and the auxiliary wings 3a are independently controlled on both sides of the body 1. If it is provided freely, the trailing edge of the rigid wing 3 or the trailing edge of the auxiliary wing 3a of the rigid wing 3 located below the airframe that has lost its posture due to the cross wind etc. Since a relatively large load can be applied to the rigid wing 3 by controlling so as to direct it, the roll axis can be quickly and easily controlled, and the normal posture can be easily restored. Alternatively, under a meteorological condition with a certain wind speed, the vertical tail 5 is adjusted so that the lift and drag generated by the wind balance with the propulsion by the propeller and the force of gravity.
It can be stopped in the air by controlling the rudder 5b, the horizontal stabilizer as an elevator 6, and the controlled parts such as the output of the prime mover.

Further, when the rigid wings 3 are mounted on both sides of the body 1 at one end and the other end at or near the side edge of the frame 2a of the seat wing 2, respectively The angle is large and the rigid wing 3 is not damaged even if the posture is slightly banked during takeoff and landing. In this case, if the rigid wing 3 is mounted on the body 1 at the prime mover case 7 which is integrated with the upper part of the body via the frame, the rigid wing 3 is located at a position considerably higher than the lower surface of the body 1. Therefore, it is more preferable.

[0023]

As described above in detail, in the radio-controlled biplane aircraft according to the present invention, the main wing is composed of the seat wing and the rigid wing, so that the stability is improved even during high speed flight and stable flight is achieved. The range of possible velocities is greatly improved, and the straightness of flight is improved against approach, crosswind, drift, turbulence, etc. during takeoff and landing. Further, various effects as described below are exhibited. It is of great value.

Since the main wing area is large, the stall speed is low and stable low-speed flight is possible, the entry angle at the time of takeoff and landing can be made steep, and there are almost no restrictions on the place of takeoff and landing. Furthermore, it is easy to maneuver and has excellent maneuverability, and it can be stopped in the air depending on the weather conditions, so that work in the sky can be performed efficiently. Therefore, as work in the sky, it is possible to perform more accurate shooting and obtain more accurate information when performing shooting and observation,
In addition, when the pilot rope is extended in the transmission line construction, the work can be performed reliably and easily, and the work efficiency is excellent.

Further, the maximum load weight can be increased because the load acting per unit area of the main wing is small as compared with the conventional radio-controlled airplane in which the main wing consists of only the seat wing or only the rigid wing.

It is capable of gliding, has a low risk of falling, and is excellent in safety.

If the rigid wings are independently controllable at the angle of attack on both sides of the fuselage, or if the rigid wings are independently controllable, they are received by the rigid wings. Since a relatively large force can be obtained by the air flow, by controlling the angle of attack of the rigid wings or the auxiliary wings so as to make a difference in the lift acting on the rigid wings on both sides of the fuselage, the roll axis Control can be performed quickly and easily.

[Brief description of the drawings]

FIG. 1 is a plan view showing an embodiment of a wirelessly controlled biplane aircraft according to the present invention.

FIG. 2 is a side view of FIG.

FIG. 3 is a front view of FIG. 1;

FIG. 4 is an explanatory view showing a rigid wing in another embodiment of the radio controlled airplane according to the present invention.

[Explanation of symbols]

 1 Body 2 Seat Wing 2a Frame 2aa Central Girder 2ab Side Girder 2ac Beam 2b Seat 3 Rigid Wing 3a Auxiliary Wing 4 Pillar 5 Vertical Tail 6 Horizontal Tail 7 Motor Case 8 Propeller 8a Propeller Guide

Claims (5)

[Claims] 1. A pillar (4) fixed to the body (1) and a vertical tail (5) are fixed to the upper center of the body (1) so that the front is elevated and is almost straight toward the rear. Beam (2aa) with a mounting surface that slopes downward in a circular pattern
And the pillars (4) fixed to the body (1) and the central girder (2
Both ends of beam (2ac) fixed to aa) and center girder (2a)
From the side girders (2ab), which are fixed to the front end of (a) and are symmetrical in a substantially C-shape on both sides in the plane, and which are inclined downward substantially linearly toward the rear. The frame (2a) and the flexible sheet material (2a fixed to the frame (2a) in a state where the frame (2a) receives the wind from the front and expands.
The main wing is composed of a seat wing (2) consisting of b) and a rigid wing (3) attached to the fuselage (1) at one end thereof at a predetermined position below the seat wing (2). Cage, torso
(1) A vertical stabilizer with a rudder (5b) swingably laterally attached to a fixed wing (5a) fixed upright at the rear end of the rear wing.
(5) and a horizontal stabilizer mounted on the fixed fin (5a) of the vertical stabilizer (5) so that the entire wing is swingable around a laterally horizontal axis.
(6) and a propeller (8) that is rotated in the vicinity of the center of gravity of the machine by a prime mover in a prime mover case (7) provided integrally with the fuselage (1). A radio-controlled biplane aircraft, wherein the output, the swing angle of the rudder (5b) of the vertical tail (5), and the swing angle of the horizontal tail (6) are wirelessly controlled. 2. The radio-controlled biplane aircraft according to claim 1, wherein the rigid wings (3) are provided so that their angles of attack can be controlled independently of each other on both left and right sides of the fuselage (1). 3. The radio-controlled biplane aircraft according to claim 1, wherein the rigid wing (3) is provided with auxiliary wings (3a) which are independently controllable on both left and right sides of the body (1). . 4. The rigid wing (3), one end of which is attached to the body (1), is attached at the other end to the side edge of the frame (2a) of the seat wing (2) or in the vicinity thereof. The radio-controlled biplane aircraft according to any one of Items 1 to 3. 5. The mounting case of the rigid wing (3) to the fuselage (1) is a prime mover case (7) which is integrated with the upper part of the fuselage main body through a frame. The radio-controlled biplane aircraft according to any one of claims 1.